Design of the low thrust transfer orbit for heliocentric space-based gravitational wave observatory

Space-based gravitational wave detection has gained attention in recent years due to its lower detection frequency. The long-term stability of configuration is critical for high-precision measurements, placing stringent demands on spacecraft orbit injection accuracy. However, during orbit transfer, uncertainty in the low thrust propulsion system's parameters accumulate over time, which may cause the spacecraft to potentially deviate from its normal orbit. This paper proposes a low thrust transfer orbit design method considering uncertainty factors for heliocentric space-based gravitational wave observatory. First, an optimization model for low thrust transfer orbit is established, using global optimization algorithm to design the nominal transfer orbit. Then, considering uncertainty in navigation and thrust, an online low thrust trajectory replanning method is proposed, which can effectively reduce end-state errors through periodic replanning. Finally, the proposed method is applied to the Taiji program. Simulation results show that after online low thrust trajectory replanning, the fuel consumption of single spacecraft is approximately 30 kg, with end-position and velocity errors of less than 4 km and 2 mm/s, respectively. This research could provide valuable references for the transfer orbit design of future Taiji program and other high-precision space science missions.